空间电推进地面综合测试评价技术研究
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摘要
推力/比冲、羽流效应及电磁兼容是空间电推进产品测试评价的主要内容。综述了光学测量法、双钟摆法、扭秤法、三丝扭摆法及电磁补偿法等方法,并提出改进的推力测量方法。对羽流等离子体基本参数、羽流离子电流密度分布、羽流离子能量分布、羽流双电荷离子比例、羽流溅射物沉积污染等羽流评价技术,经方案对比提出了现阶段最适宜的测试方法,分别是朗缪尔探针、法拉第探针、RPA、E×B探针、QCM等方法。电磁兼容性测试领域,根据电推进的工作特点,提出了基于透波副舱的实验方法。为空间电推进地面综合测试评价提供方法和测试手段。
Space thrust and specific impulse,plume effects,electromagnetic compatibility are the key performances of an electric propulsion system in space applications. This paper summarizes the micro-thrust measurement methods,such as optical measurement,doubles bell pendulum method,torsion scale method,three wire torsion pendulum method and electromagnetic compensation method. Then the modified thrust measurement method is proposed. For measuring the basic parameters of plume,ion current density distribution,ion energy distribution,doubly charged ions radio,plume sputtering deposition and so on,the corresponding measurement methods,the Langmuir probe,Faraday probe,RPA,E × B probe,QCM and other corresponding measurement methods,can be applied. In the field of electromagnetic compatibility test,according to the working characteristics of electric propulsion,an experimental method based on transdermal wave sub-chamber is proposed. In a word,the method for the ground evaluation of space electric is provided.
Space thrust and specific impulse,plume effects,electromagnetic compatibility are the key performances of an electric propulsion system in space applications. This paper summarizes the micro-thrust measurement methods,such as optical measurement,doubles bell pendulum method,torsion scale method,three wire torsion pendulum method and electromagnetic compensation method. Then the modified thrust measurement method is proposed. For measuring the basic parameters of plume,ion current density distribution,ion energy distribution,doubly charged ions radio,plume sputtering deposition and so on,the corresponding measurement methods,the Langmuir probe,Faraday probe,RPA,E × B probe,QCM and other corresponding measurement methods,can be applied. In the field of electromagnetic compatibility test,according to the working characteristics of electric propulsion,an experimental method based on transdermal wave sub-chamber is proposed. In a word,the method for the ground evaluation of space electric is provided.
引文
[1]Cassady L D,Kodys A D,Choueiri E Y.A thrust stand for highpower steady-state plasma thrusters[C]//38th AIAA Joint Propulsion Conference,number AIAA.2002,4118:7-10.
[2]Ziemer J K.Performance measurements using a sub-micronewton resolution thrust stand[J].IEPC,2001.
[3]Gamero-Casta?o M,Hruby V,Martínez-Sánchez M.A torsional balance that resolves sub-micro-Newton forces[C]//27th International Electric Propulsion Conference,Pasadena,CA,2001:15-19.
[4]Lake J P,Cavallaro G,Spanjers G,et al.Resonant operation of a micro-Newton thrust stand[R].Air Force Research Lab Edwards Afb Ca Space and Missile Propulsion Div,2003.
[5]Cifali G,Misuri T,Rossetti P,et al.Preliminary characterization test of HET and RIT with Nitrogen and Oxygen[C]//Proceedings of the 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,San Diego,2011.
[6]宁中喜,范金蕤.三丝扭摆微推力在线测量方法及不确定度分析[J].测控技术,2012,31(5):45-48.
[7]汤海滨,刘宇,赵宝瑞,等.一种电推力器用小推力测量系统[J].推进技术,2001,22(2):174-176.
[8]Day M,Maslennikov N,Randolph T,et al.SPT-100 subsystem qualification status[C]//Proc 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conf Exhibit,1996:10-12.
[9]Rattenni,Jr L.Design and performance of the Orbital Star-2propulsion subsystem[C]//37th Joint Propulsion Conference and Exhibit,2001:3394.
[10]Otsap B,Cardin J,Sarver-Verhey T,et al.Photo-Chemically Etched Construction Technology for Digital Xenon Feed Systems[C]//USA:Electric Rocket Propulsion Society,2001.
[11]Schappell D T,Sankovic J M.The BMDO SBIR program,a magnetostrictive actuated,multi-function xenon gas valve[R].AIAA,1998:3496.
[12]Pehrson D M.Continuing Development of the Proportional Flow Control Valve(PFCV)for Electric Propulsion Systems[C]//30th International Electric Propulsion Conference,Florence,Italy,2007.
[13]Matticari G,Noci G E,Siciliano P,et al.Next generation propellant flow control components for electric propulsion systems:Status of achievements at Alcatel Alenia Space Italia/Laben-Proel[C]//IEPC,2005:23.
[14]Schappell D,Mc Lean C.Multi-function valve extended development testing[C]//35th Joint Propulsion Conference and Exhibit,1999:2561.
[15]Johannessen J A.The Four Candidate Earth Explorer Core Missions:Gravity Field and Steady State Ocean Circulation Mission[C]//ESA Publ Division,1999.
[16]胡竟,杨福全,孙运奎,等.用多孔塞片实现推进剂微小流率的控制[J].航天器环境工程,2015,32(1):95-98.
[17]张涤新,郭美如,冯焱,等.定容式流导法微流量校准装置[J].真空科学与技术学报,2005,25(1):21-25.
[18]Keefer D,Semak V V.Measurements of radial and axial distributions of ion thruster plasma parameters using a Langmuir probe[R].AIAA Paper,1996.
[19]Pacros A A E.Instruments design and testing for a Hall thruster plume experiment on the space shuttle[D].Massachusetts Institute of Technology,2002.
[20]Byrne L,Gatsonis N,Pencil E.Triple Langmuir probe measurements in the plume and backflow region of a pulsed plasma thruster[C]//37th Joint Propulsion Conference and Exhibit,2001:3640.
[21]Warner N Z.Performance testing and internal probe measurements of a high specific impulse hall thruster[D].Massachusetts Institute of Technology,2003.
[22]Azziz Y.Instrument development and plasma measurements on a 200-watt Hall thruster plume[D].Massachusetts Institute of Technology,2003.
[23]Haas J M.Low-perturbation interrogation of the internal and near-field plasma structure of a Hall thruster using a highspeed probe positioning system[M].University of Michigan,2001.
[24]Hofer R R,Thesis P D.The development and characterization of High-efficiency,High-specific Impulse Xenon Hall Thruster[D].University of Michigan,Department of Aerospace Engineering,2004.
[25]Glover T W.Measurement of plasma parameters in the exhaust of a magnetoplasma rocket by gridded energy analyzer and emissive Langmuir probe[D].Rice University,2002.
[26]Pollard J.Plume angular,energy,and mass spectral measurements with the T5 ion engine[C]//Joint Propulsion Conference and Exhibit,2013.
[27]Kim S W.Experimental investigations of plasma parameters and species-dependent ion energy distribution in the plasma exhaust plume of a Hall thruster[D].University of Michigan,1999.
[28]King L B.Transport-property and mass spectral measurements in the plasma exhaust plume of a Hall-effect space propulsion system[D].University of Michigan,1998.
[29]Foster J E,Soulas G C,Patterson M J.Plume and discharge plasmameasurementsofannstar-typeionthruster[R].AIAA,2000.
[30]Walker M L R.Effects of facility backpressure on the performance and plume of a Hall thruster[M].University of Michigan,2005.
[31]Hofer R R,Walker M L R,Gallimore A D.A Comparison of nude and collimated Faraday Probes for Use with Hall Thrusters[C]//27th International Electric Propulsion Conference.Fairview Park,OH:Electric Rocket Propulsion Soc,2001:15-19.
[32]Walker M,Hofer R,Gallimore A.The effects of nude Faraday probe design and vacuum facility backpressure on the measured ion current density profile of Hall thruster plumes[R].AIAA,2002.
[33]Kamhawi H,Soulas G C,Patterson M J,et al.NEXT ion engine 2000 hour wear test plume and erosion results[J].AIAA Paper,2004:3792.
[34]Peterson P Y,Thesis P D.The development and characterization of a two-stage Hybrid Hall/Ion Thruster[D].University of Michigan,Department of Aerospace Engineering,2004.
[35]唐福俊.离子推力器推力矢量偏角测试[J].真空与低温,2009,15(2):81-85.
[36]King L B,Gallimore A D.Ionic and Neutral Particle Transport Property measurements in the Plume of an SPT-100[C]//32nd Joint Propulsion Conference,Lake Buena Vista,1996.
[37]Beal B E,Gallimore A D.Energy analysis of a Hall thruster cluster[J].Ann Arbor,2003,1001:48109.
[38]Kim S W,Gallimore A D.Plume study of a 1.35-k W SPT-100 using an Ex B probe[J].Journal of Spacecraft and Rockets,2002,39(6):904-909.
[39]Williams Jr G J,Domonkos M T,Chavez J M.Measurement of doubly charged ions in ion thruster plumes[C]//IEPC,2002.
[40]Vahrenkamp R P.Measurement of double charged ions in the beam of a 30 cm mercury bombardment thruster[R].AIAA,1973.
[41]唐福俊,张天平.离子推力器羽流测量E×B探针设计及误差分析[J].真空与低温,2007,13(2):77-80.
[42]颜则东,张剑锋,柏树,等.电推进羽流污染物分析[J].真空与低温,2011,17(s2):177-180.
[43]李林凌,刘伟,赵烁.电推进系统空间试验技术研究[J].航天器工程,2014,23(3):126-132.
[2]Ziemer J K.Performance measurements using a sub-micronewton resolution thrust stand[J].IEPC,2001.
[3]Gamero-Casta?o M,Hruby V,Martínez-Sánchez M.A torsional balance that resolves sub-micro-Newton forces[C]//27th International Electric Propulsion Conference,Pasadena,CA,2001:15-19.
[4]Lake J P,Cavallaro G,Spanjers G,et al.Resonant operation of a micro-Newton thrust stand[R].Air Force Research Lab Edwards Afb Ca Space and Missile Propulsion Div,2003.
[5]Cifali G,Misuri T,Rossetti P,et al.Preliminary characterization test of HET and RIT with Nitrogen and Oxygen[C]//Proceedings of the 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,San Diego,2011.
[6]宁中喜,范金蕤.三丝扭摆微推力在线测量方法及不确定度分析[J].测控技术,2012,31(5):45-48.
[7]汤海滨,刘宇,赵宝瑞,等.一种电推力器用小推力测量系统[J].推进技术,2001,22(2):174-176.
[8]Day M,Maslennikov N,Randolph T,et al.SPT-100 subsystem qualification status[C]//Proc 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conf Exhibit,1996:10-12.
[9]Rattenni,Jr L.Design and performance of the Orbital Star-2propulsion subsystem[C]//37th Joint Propulsion Conference and Exhibit,2001:3394.
[10]Otsap B,Cardin J,Sarver-Verhey T,et al.Photo-Chemically Etched Construction Technology for Digital Xenon Feed Systems[C]//USA:Electric Rocket Propulsion Society,2001.
[11]Schappell D T,Sankovic J M.The BMDO SBIR program,a magnetostrictive actuated,multi-function xenon gas valve[R].AIAA,1998:3496.
[12]Pehrson D M.Continuing Development of the Proportional Flow Control Valve(PFCV)for Electric Propulsion Systems[C]//30th International Electric Propulsion Conference,Florence,Italy,2007.
[13]Matticari G,Noci G E,Siciliano P,et al.Next generation propellant flow control components for electric propulsion systems:Status of achievements at Alcatel Alenia Space Italia/Laben-Proel[C]//IEPC,2005:23.
[14]Schappell D,Mc Lean C.Multi-function valve extended development testing[C]//35th Joint Propulsion Conference and Exhibit,1999:2561.
[15]Johannessen J A.The Four Candidate Earth Explorer Core Missions:Gravity Field and Steady State Ocean Circulation Mission[C]//ESA Publ Division,1999.
[16]胡竟,杨福全,孙运奎,等.用多孔塞片实现推进剂微小流率的控制[J].航天器环境工程,2015,32(1):95-98.
[17]张涤新,郭美如,冯焱,等.定容式流导法微流量校准装置[J].真空科学与技术学报,2005,25(1):21-25.
[18]Keefer D,Semak V V.Measurements of radial and axial distributions of ion thruster plasma parameters using a Langmuir probe[R].AIAA Paper,1996.
[19]Pacros A A E.Instruments design and testing for a Hall thruster plume experiment on the space shuttle[D].Massachusetts Institute of Technology,2002.
[20]Byrne L,Gatsonis N,Pencil E.Triple Langmuir probe measurements in the plume and backflow region of a pulsed plasma thruster[C]//37th Joint Propulsion Conference and Exhibit,2001:3640.
[21]Warner N Z.Performance testing and internal probe measurements of a high specific impulse hall thruster[D].Massachusetts Institute of Technology,2003.
[22]Azziz Y.Instrument development and plasma measurements on a 200-watt Hall thruster plume[D].Massachusetts Institute of Technology,2003.
[23]Haas J M.Low-perturbation interrogation of the internal and near-field plasma structure of a Hall thruster using a highspeed probe positioning system[M].University of Michigan,2001.
[24]Hofer R R,Thesis P D.The development and characterization of High-efficiency,High-specific Impulse Xenon Hall Thruster[D].University of Michigan,Department of Aerospace Engineering,2004.
[25]Glover T W.Measurement of plasma parameters in the exhaust of a magnetoplasma rocket by gridded energy analyzer and emissive Langmuir probe[D].Rice University,2002.
[26]Pollard J.Plume angular,energy,and mass spectral measurements with the T5 ion engine[C]//Joint Propulsion Conference and Exhibit,2013.
[27]Kim S W.Experimental investigations of plasma parameters and species-dependent ion energy distribution in the plasma exhaust plume of a Hall thruster[D].University of Michigan,1999.
[28]King L B.Transport-property and mass spectral measurements in the plasma exhaust plume of a Hall-effect space propulsion system[D].University of Michigan,1998.
[29]Foster J E,Soulas G C,Patterson M J.Plume and discharge plasmameasurementsofannstar-typeionthruster[R].AIAA,2000.
[30]Walker M L R.Effects of facility backpressure on the performance and plume of a Hall thruster[M].University of Michigan,2005.
[31]Hofer R R,Walker M L R,Gallimore A D.A Comparison of nude and collimated Faraday Probes for Use with Hall Thrusters[C]//27th International Electric Propulsion Conference.Fairview Park,OH:Electric Rocket Propulsion Soc,2001:15-19.
[32]Walker M,Hofer R,Gallimore A.The effects of nude Faraday probe design and vacuum facility backpressure on the measured ion current density profile of Hall thruster plumes[R].AIAA,2002.
[33]Kamhawi H,Soulas G C,Patterson M J,et al.NEXT ion engine 2000 hour wear test plume and erosion results[J].AIAA Paper,2004:3792.
[34]Peterson P Y,Thesis P D.The development and characterization of a two-stage Hybrid Hall/Ion Thruster[D].University of Michigan,Department of Aerospace Engineering,2004.
[35]唐福俊.离子推力器推力矢量偏角测试[J].真空与低温,2009,15(2):81-85.
[36]King L B,Gallimore A D.Ionic and Neutral Particle Transport Property measurements in the Plume of an SPT-100[C]//32nd Joint Propulsion Conference,Lake Buena Vista,1996.
[37]Beal B E,Gallimore A D.Energy analysis of a Hall thruster cluster[J].Ann Arbor,2003,1001:48109.
[38]Kim S W,Gallimore A D.Plume study of a 1.35-k W SPT-100 using an Ex B probe[J].Journal of Spacecraft and Rockets,2002,39(6):904-909.
[39]Williams Jr G J,Domonkos M T,Chavez J M.Measurement of doubly charged ions in ion thruster plumes[C]//IEPC,2002.
[40]Vahrenkamp R P.Measurement of double charged ions in the beam of a 30 cm mercury bombardment thruster[R].AIAA,1973.
[41]唐福俊,张天平.离子推力器羽流测量E×B探针设计及误差分析[J].真空与低温,2007,13(2):77-80.
[42]颜则东,张剑锋,柏树,等.电推进羽流污染物分析[J].真空与低温,2011,17(s2):177-180.
[43]李林凌,刘伟,赵烁.电推进系统空间试验技术研究[J].航天器工程,2014,23(3):126-132.